An aircraft gas turbine engine nacelle comprising a thrust reversal arrangement. The thrust reversal arrangement comprises at least one thrust reverser cascade box comprising a fixed structure and a plurality of thrust reverser vanes configured to direct bypass air forwardly. At least a subset of the thrust reverser vanes are pivotable and/or translatable relative to the fixed structure between a deployed position, in which the vanes define a first volume, and a stowed position, in which the pivotable vanes define a second, smaller volume.


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    Title :

    AIRCRAFT GAS TURBINE ENGINE NACELLE


    Contributors:

    Publication date :

    2018-02-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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